Abstract: The hybrid tape includes an outer member that is formed with a material having desirable tensile qualities, such that the outer member is tailored to exhibit superior fatigue performance in tension induced from bending. The hybrid tape further includes an inner member that is formed with a material having desirable compression qualities, such that the inner member is tailored to exhibit superior fatigue performance in compression induced from bending. The hybrid tape is configured such that the bend neutral axis is located between the inner material and the outer material, thereby insuring the outer material only experiences tension in bending while the inner material only experiences compression in bending.

Abstract: An apparatus for attaching a member to a honeycomb core-stiffened structure includes a body and one or more elements extending from the body configured to be adhesively bonded to one or more walls of a honeycomb core of the honeycomb core-stiffened structure. The apparatus further includes a fitting for attaching the member to the apparatus. A honeycomb core-stiffened structure includes a honeycomb core and an apparatus for attaching a member to the honeycomb core. The apparatus includes a body and one or more elements extending from the body configured to be adhesively bonded to one or more walls of the honeycomb core of the honeycomb core-stiffened structure. The apparatus further includes a fitting for attaching the member to the apparatus.

Abstract: An aircraft includes a surface over which an airflow passes. A plasma actuator is configured to generate a plasma above the surface, the plasma coupling a directed momentum into the air surrounding the surface to reduce separation of the airflow from the surface. A method of reducing separation of an airflow from a surface of an aircraft includes generating a plasma in air surrounding the surface at a position where the airflow would separate from the surface in the absence of the plasma.

Abstract: A system and method to control fuselage torque of an aircraft. The system includes a tail boom having a first surface that creates a high-pressure region in a downward rotorwash and a second surface that creates a low-pressure region in the downward rotorwash. The difference in pressure regions creates a lateral force that opposes the fuselage torque.

Abstract: A vibration isolator having an upper housing defining an upper fluid chamber, a lower housing defining a lower fluid chamber, a piston resiliently disposed within the upper housing and the lower housing, a tuning passage defined by the piston, for providing fluid communication between the upper fluid chamber and the lower fluid chamber, a tuning fluid disposed within the tuning passage, the upper fluid chamber, and the lower fluid chamber. A reservoir in fluid communication with the upper fluid chamber for providing pressurization control of the vibration isolator. An expanded accumulator region for providing Increased pressure retention during maintenance and operation of the vibration isolator.

Abstract: A cable puller assembly includes a housing assembly, a motor assembly and an anti-fouling device. The motor assembly is secured to the housing assembly and has an output shaft extending outwardly therefrom. The output shaft is rotated about an axis of rotation by the motor assembly. The anti-fouling device has a capstan and a body. The output shaft is operatively associated with the capstan in order to rotate the capstan about the axis of rotation. The body is positioned around an end portion of the capstan proximate to the housing assembly. The body defines a sloped surface that biases incoming rope that wraps around the sloped surface down onto the capstan.

Abstract: A fuel vapor storage and recovery apparatus includes a fuel vapor storage canister, said fuel vapor storage canister comprising at least first and second vapor storage compartments filled with an absorbent material, for instance filled with activated carbon, at least a vapor inlet port, an atmospheric vent port and a purge port. Said fuel vapor storage canister defines an air flow path between said vapor inlet port and said atmospheric vent port during shut-off of the internal combustion engine of the vehicle. During purging cycles there is defined an air flow path between said atmospheric vent port and said purge port wherein said first and second vapor storage compartments are arranged in concentric relationship and wherein said first and second vapor storage compartments in flow direction are separated from each other by an air gap diffusion barrier.

Abstract: A ducted fan for a helicopter includes a transverse duct and a counter-torque device supported within the duct. The counter-torque device includes a rotor rotatably mounted within the duct and a stator fixedly mounted within the duct downstream from the rotor. The rotor includes a rotor hub having a rotor axis, and rotor blades extending from the hub. The Rotor blades have a modulated angular distribution about the rotor axis. The stator includes a stator hub, and a plurality of stator vanes distributed around the stator hub. The stator vanes are angularly modulated around the stator hub.

Abstract: The invention relates to a method for producing hollow bodies from thermoplastic material in which web- or strip-type preforms of plasticised plastics material are shaped in a multi-part tool which forms a mould nest, with two outer moulds and a central mould which perform opening and closing movements with respect to one another. The central mould is provided with at least one device for receiving and manipulating components to be fastened in the interior of the hollow body by means of a material and/or form-fitting joint. Prior to the fastening of the components to the inner wall of the hollow body to be produced, the components are heated by means of a radiant heating device. The radiant heating device is advantageously integrated in the central mould of the tool.

Abstract: A pitch control system for blades on a rotor of an aircraft has a gimballing rotor hub (31) and a plurality of step-over arms (61) connected to the hub and capable of pivoting relative to the hub about a pivot axis. Each of a plurality of pitch links (55) connects one of the step-over arms (61) to a flight control system for pivoting the connected step-over arm (61) about the pivot axis and relative to the hub in response to inputs from the control system. Each of a plurality of step-over links (69) connects one of the step-over arms (61) to one of the blades for rotating the associated blade about the pitch axis in response to pivoting of the associated step-over arm.

Abstract: The invention concerns a process for the production of a container, in particular a fuel tank of thermoplastic material, by extrusion blow molding, wherein during shaping of the container within a multi-part tool the container is provided with at least one connecting element passing through the wall thereof, wherein with at least a part of the connecting element as a lost shaping male die the wall of the container is displaced from one side into a tool placed on the oppositely side of the container wall and removed. The invention further concerns a fuel tank with at least one connecting element which is connected to the tank wall at least in region-wise manner by intimate joining of the materials involved.

Abstract: An aircraft includes a heat absorbent material carried by an airfoil susceptible to ice buildup and a transmitter spaced apart from the heat absorbent material. A method includes the process of transmitting the heat energy from the transmitter to the heat absorbent material that in turn warms the airfoil to break apart ice buildup.

Abstract: A method for evaluating the integrity of a cable shield utilizing wideband noise-to-ground measurements is provided. Upon determining that trouble with the cable shield exists, a method s is provided to isolate the location of the trouble with the cable shield. The method utilizes access locations along the cable and therefore does not require opening of the cable shield to isolate the trouble in the shield.

Abstract: A lubrication system includes a reserve housing configured to retain a lubrication fluid. A supply line in fluid communication with the reserve housing is configured to provide pressurized lubrication fluid to the reserve housing. An overflow tube has an overflow port, the overflow tube being configured to prevent the volume of the lubrication fluid from exceeding a certain amount. A metering jet is configured to allow the lubrication fluid to flow from the reserve housing onto a component, such as a bearing, in the gearbox at a predetermined rate. The metering jet provides flow of the lubrication fluid onto the bearing even when the supply line no longer provides pressurized lubrication fluid to the reserve housing.

Abstract: A tube form assembly includes an inner member and an outer member. Each of the inner and outer members has an offset which creates a cavity therebetween. During assembly of the tube form assembly, an adhesive is located in the cavity and squeezed out and through the adjacent bond lines between the inner member and outer member. The pressurization and flow of adhesive outward from the cavity facilitates removal of air bubbles, as well as prevents the introduction of air bubbles into the bond line.

Abstract: An aircraft and method to control flat yawing turns of the aircraft while maintaining a constant vector across a ground surface. The aircraft includes a control system in data communication with control actuators, a lateral control architecture, a longitudinal control architecture, and an initialization command logic. The lateral control architecture controls the aircraft in the lateral direction, while the longitudinal control architecture controls the aircraft in the longitudinal direction. The initialization command logic automatically activates the lateral control architecture and the longitudinal control architecture to maintain a constant vector across the ground whenever a directional control input is made at low speed.

Abstract: A self-retaining anti-rotation clip for a spherical-bearing rod end has two opposing spacer plates, each spacer plate having a curved edge portion for surrounding at least a portion of a ball of the rod end. A connector plate connects the spacer plates, such that the spacer plates are spaced from each other and generally parallel to each other. Retaining means are carried on the clip and adapted for retaining each spacer plate in a position generally adjacent one side of a body of the rod end, such that the spacer plates are free from interference with the ball of the rod end.

Abstract: The invention relates to a method for producing a fuel container and to a fuel container for motor vehicles.

Abstract: A regeneration energy shunt system utilizes a module to monitor the power bus voltage and can divert excess regeneration energy to a resistor array to dissipate the excess regeneration energy. The module can monitor the state of charge of a rechargeable power source to ascertain when excess regeneration energy condition exists. The resistor array can include a plurality of resistors. The module can ascertain the number of resistors needed dissipate the excess regeneration energy and selectively direct the excess regeneration energy to the required number of resistors. The module can dynamically switch which resistors are used to dissipate the excess regeneration energy and can thereby even out the loading across the resistors. The module can ascertain a state of health of the individual resistors and remove unhealthy resistors from service, report the state of health of the resistors, and initiate changes in operation based thereon.